EP1964774A2 - Flying device with rotating cylinders for generating lift and/or thrust - Google Patents
Flying device with rotating cylinders for generating lift and/or thrust Download PDFInfo
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- EP1964774A2 EP1964774A2 EP08003540A EP08003540A EP1964774A2 EP 1964774 A2 EP1964774 A2 EP 1964774A2 EP 08003540 A EP08003540 A EP 08003540A EP 08003540 A EP08003540 A EP 08003540A EP 1964774 A2 EP1964774 A2 EP 1964774A2
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- aircraft according
- rotor blades
- cylinder
- aircraft
- fan
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- 238000010009 beating Methods 0.000 claims description 6
- 125000004122 cyclic group Chemical group 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 8
- 239000013598 vector Substances 0.000 description 4
- 230000024703 flight behavior Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
- B64C39/005—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a horizontal transversal axis
Definitions
- the present invention relates to an aircraft with a payload sump on which rotating about transverse axes with controllable speed driven closed cylinder for generating lift and / or propulsion are arranged according to the Magnus bin.
- Object of the present invention is to provide an aircraft according to the preamble of claim 1 in such a way that it has vertical or Kurzstarteigenticianen.
- each cylinder is associated with an adjustable drive power to produce a transverse air flow stream.
- a force vector can thus be generated in different directions of the aircraft, ie also in the direction of the vertical axis, and it is thus possible to implement a vertically-starting or short-starting aircraft.
- an inventive aircraft Compared to known short-start or vertical takeoff aircraft, such.
- Tiltrotorflugmaschine or the helicopter an inventive aircraft has significant advantages. So z. B. not, as in the helicopter, a tilt of the rotor plane necessary to change the marching speed; the problems of rotor blades in helicopters, especially in high-performance helicopters, by reaching the speed of sound of the blade tips fall away; on a balancing rotor, such as the usual tail rotor in helicopters can be omitted.
- a major advantage of the aircraft according to the invention should be emphasized that a change in the Queranströmung the rotating cylinder size and direction with technically inexpensive means can be realized and thus particularly agile flight behavior of the aircraft is achievable.
- any type of fan can be used for the transverse flow of the rotating cylinder, so z.
- a propeller blower or an axial fan in the manner of a so-called fans as used in modern jet engine aircraft is used, is as a preferred embodiment of the invention proposed to use a radial fan, the wing profile having rotor blades are pivotable about axes aligned parallel to the axis of rotation. This configuration has excellent opportunities to control the cross flow size and direction exactly.
- a rotor assembly for generating buoyancy and / or propulsion forces which is also designed as a radial fan with profiled wing rotor blades.
- the aforementioned document mainly relates to the control method for changing the angle of attack of the rotor blades of the radial fan. Also, this document is not indicative of the application of the Magnus effect.
- the invention undergoes the fact that the rotor of the radial fan surrounds each concentrically surrounding the rotating cylinder to be flowed in at a distance.
- the radial distance of the rotating rotor blades from the mantle surface of the closed rotating cylinder should be one to two times the tread depth of the rotor blades.
- the diameter of the radial fan motor in turn should amount to five to eight times the tread depth of a rotor blade according to a preferred embodiment of the invention.
- the number of rotor blades to be used for a radial fan rotor should be at least two, preferably eight. It should be at least as large as the tread depth of the rotor blades in a further embodiment of the invention, the circumferential distance of the rotor blades of the radial fan.
- angles of incidence of the rotor blades of the radial fan are controlled periodically with the rotation.
- the control of the angle of attack of the rotor blades takes place centrally by an eccentric crank with extending to the individual rotor blades control rods.
- a control of the angle of attack of the rotor blades via a control gear can take place, which comprises a rotating about the rotor axis of the radial fan drive wheel and cooperating with this radially extending to each individual rotor blade control shafts.
- the latter embodiment is particularly advantageous when high flow velocities and thus comparatively high speeds of rotation of the radial fan are to be realized.
- the rotor blades of the radial fan are designed to change the wing profile in several parts.
- Such Training is particularly advantageous if an operation at low flow velocities is taken into consideration.
- both the direction of rotation of the closed cylinder should be changeable and the rotational speed of the closed cylinder should be adjustable independently of the rotational speed of the radial fan.
- an aircraft symmetrical to Nutzlastrumpf arranged on both sides of cross-flow fan and rotating cylinder existing drive units. Due to their precise control, a pivoting of the aircraft can be adjusted about its longitudinal axis when turning. Finally, it is advantageous if an aircraft has at least two drive unit pairs which are spaced apart from each other in the longitudinal direction and comprise cross-flow fans and rotating cylinders.
- Fig. 1 shown in the oblique image aircraft comprises a Nutzlastumpf 30 to the four drive units 40 are arranged to generate buoyancy and / or propulsion forces.
- the main axes of the aircraft 30 are a longitudinal axis L, a transverse axis Q and a vertical axis H.
- two drive units 40 form a pair of drive units and are symmetrical with respect to the longitudinal axis L of the aircraft.
- Each drive unit 40 comprises, in Fig. 1 no longer shown, a closed rotating cylinder for generating the buoyancy or propulsive forces after the Magnus effect and a him associated with it, transversely flowing fan.
- One of the rotational axes of a drive unit 40 is designated by 19.
- Fig. 2 one of the drive units 40 is shown schematically. It consists of a rotating closed cylinder 1, which rotates about the axis of rotation 19 according to the registered arrow.
- the cylinder 1 is flowed transversely according to the arrow directions 8 of a fan 2, which is shown stylized by a propeller blades.
- a driving force which is aligned substantially transversely to the direction of flow 8.
- Fig. 2a is one of the FIG. 2 similar arrangement shown, with the blower 2 is located in the flow direction 8 behind the closed cylinder 1 here.
- a third embodiment of the drive units 40 is shown schematically. It consists of a rotating closed cylinder 1, which rotates about the axis of rotation 19 according to the registered arrow.
- the cylinder 1 is flowed transversely according to the arrow directions 8 from a fan 2, which is shown stylized by a beating wing 22.
- the beating wing moves translationally without angle change in the direction of the arrow tr transverse to the direction of the flow to be generated 8 up and down between the end positions 22a and 22b.
- the impulse to the flow medium results from the airfoil profile of the wing 22. Instead of only one wing 22, several of which may be arranged in the manner of a wing grid.
- a fourth embodiment of the drive units 40 is shown schematically. It consists of a rotating closed cylinder 1, which rotates about the axis of rotation 19 according to the registered arrow.
- the cylinder 1 is flowed transversely according to the arrow directions 8 of a fan 2, which is shown stylized by a beating wing 220.
- the beating wing 220 performs a cyclic movement between the end positions 220 a and 220 b, which comprises a translational transverse movement according to the indicated arrow direction tr and a rotational movement about the axis 221.
- a plurality of wings 220 may be provided.
- the in the Fig. 3a and 3b shown drive unit in turn consists of a central closed (by means not shown drive means) in rotation offset cylinder 1, around which concentrically a radial fan with eight rotor blades 23 is arranged.
- the angle of attack ⁇ of the rotor blades 23 is variable by means of control rods 24, wherein a cyclical change of the angle of attack ⁇ of the rotor blades is achieved by articulation of the control rods 24 on an eccentric crank 25.
- a comparison of Fig. 3a with the Fig. 3b shows the change in the angle of attack of the rotor blades 23 and thus the change in the force vectors 26 on the rotor blades.
- the radial distance of the rotating rotor blades 23 from the cylinder 1 is designated by a.
- Fig. 4 which are essentially the representation of the Fig. 3a and 3b is similar, in addition to the elements cylinder 1 and 2 radial fan with the rotor blades 23, control rods 24 and the fulcrum of the eccentric crank 25 is still shown the direction 8 of the flow generated by the radial fan 2, the force vectors 26 of the rotor blades, the direction of rotation 17 of the cylinder 1, the direction of rotation 21 of the radial fan 2 and the force vector 10 of the drive unit due to the flow 8 and the Rotation 17 comes about.
- Fig. 5 schematically shows a control gear for controlling the angle of attack ⁇ of the rotor blades 23 of the radial fan 2.
- a rotating about the axis of rotation 19 of the radial fan 2 drive wheel 27 drives to each individual rotor blade 23 extending control shafts 28 and allows a central adjustment of the angle ⁇ .
- Fig. 6 shows the multi-part design of the rotor blades 23, wherein in the embodiment shown, each rotor blade is formed in two parts with a first portion 23a and a second blade portion 23b, each portion about an axis parallel to the axis of rotation 19 axis 230a, 230b is pivotable and by concave / convex mesh the rotor blade sections 23a, 23b and an articulation of the control rod 24 on the rotor blade section 23b, the rotor blade geometry is variable.
- FIGS. 7 and 8 correspond to the illustration below Fig. 1 and show further embodiments of an aircraft according to the invention.
- the central payload hull 30 laterally support structures 31, 32 integrally formed, which also serve for the storage of the rotating cylinder and cross-flow fan drive units 40.
- the support structures 31, 32 are equipped with a wing-like profile 33 at least in their front area.
- FIG. 8 illustrated further embodiment of an aircraft according to the invention has symmetrically on the central payload hull 30 arranged wing-like support structures 35, 36, each fork-shaped in the direction of flight and against the direction of flight and record each between the legs of a rotating cylinder and cross-flow fan drive unit 40 record.
- the central regions of the support structures 35, 36 are preferably in turn equipped with a wing contour 37.
- the oblique image representation according to Fig. 9 corresponds to the representation of the cylinder 1 to Fig. 2 to Fig. 2c and shows a further embodiment of a cylinder 1 rotating about the axis 19 with three disks 29 whose diameter is greater than the cylinder diameter di.
- the 1 ⁇ 2 x (da-di) bulkhead walls protruding outward from the cylinder jacket increase the aerodynamic efficiency of the drive unit. It does not have, as in Fig. 9 shown to be provided with three panes or bulkhead walls; already by a disc or bulkhead can be achieved improvements in aerodynamics. Also z. B. only the two end plates can be provided on the cylinder 1.
- the schematic oblique image according to Fig. 10 shows a drive unit 40 with a radial fan, which comprises two rotor blades 23 and a control rod 24.
- the rotational circle of the rotor blades 23 has such a distance a 1 from the outer edge of the discs 29 that, during the permitted pivotal movement of the rotor blades, no contact of the discs 29 takes place during operation.
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Abstract
Description
Die vorliegende Erfindung bezieht sich auf ein Fluggerät mit einem Nutzlastrumpf an dem um Querachsen rotierende mit steuerbarer Drehzahl antreibbare geschlossene Zylinder zur Erzeugung von Auftrieb und/oder Vortrieb nach dem Magnuseffekt angeordnet sind.The present invention relates to an aircraft with a payload sump on which rotating about transverse axes with controllable speed driven closed cylinder for generating lift and / or propulsion are arranged according to the Magnuseffekt.
Ein Fluggerät der vorbezeichneten Bauart ist aus dem Internet http://de.wikipedia.org/wiki/Rotorflugzeug bekannt. Wie beim historischen Rotorschiff von Flettner rotierende Zylinder zur Erzeugung von Vortrieb benutzt wurden, werden bei dem vorbekannten Rotorflugzeug die rotierenden Zylinder unter Ausnutzung des Magnuseffektes zur Erzeugung von Auftrieb benutzt. Obwohl die durch den Magnuseffekt erzielbaren Auftriebskräfte beachtliche Werte erreichen können, ist Voraussetzung dafür doch die Queranströmung der rotierenden Zylinder. Demzufolge kann bei dem vorbekannten Rotorflugzeug Auftrieb nur dann erzeugt werden, wenn, wie bei herkömmlichen Starrflügelflugzeugen durch hohe Vortriebsleistungen, eine beachtliche Marschgeschwindigkeit erreicht wurde. Demzufolge kann das vorbekannte Rotorflugzeug keine Kurzstart- oder gar Senkrechtstarteigenschaft aufweisen.An aircraft of the aforementioned type is known from the Internet http://de.wikipedia.org/wiki/Rotorflugzeug . As with the historic rotorcraft of Flettner rotating cylinders were used to generate propulsion, in the known rotor aircraft, the rotating cylinder using the Magnus effect used to generate lift. Although the buoyancy forces that can be achieved by the Magnus effect can reach considerable values, the prerequisite for this is the transverse flow of the rotating cylinders. Consequently, in the previously known rotor aircraft lift can only be generated if, as in conventional fixed-wing aircraft by high propulsion power, a considerable marching speed was reached. As a result, the prior art rotor aircraft can not have a short-start or even a vertical-start characteristic.
Aufgabe der vorliegenden Erfindung ist es, ein Fluggerät nach dem Oberbegriff des Patentanspruchs 1 so auszubilden, dass es Senkrecht- oder Kurzstarteigenschaften aufweist.Object of the present invention is to provide an aircraft according to the preamble of
Erfindungsgemäß wird die gestellte Aufgabe von einem Fluggerät mit den Merkmalen des Patentanspruchs 1 gelöst. Demnach ist bei einem gattungsgemäßen Fluggerät jedem Zylinder zur Erzeugung eines in quer anströmenden Luftstromes ein Gebläse mit einstellbarer Antriebsleistung zugeordnet.According to the invention this object is achieved by an aircraft with the features of
Durch die unmittelbare Kombination von Gebläse mit dem rotierenden Zylinder zur Ausnutzung des Magnuseffekts kann somit ein Kraftvektor in unterschiedliche Richtungen des Fluggeräts, also auch in Richtung der Hochachse, erzeugt werden und es kann damit ein senkrecht startendes oder kurz startendes Fluggerät verwirklicht werden.As a result of the direct combination of fan with the rotating cylinder for utilizing the Magnus effect, a force vector can thus be generated in different directions of the aircraft, ie also in the direction of the vertical axis, and it is thus possible to implement a vertically-starting or short-starting aircraft.
Gegenüber bekannten Kurzstart- oder Senkrechtstartfluggeräten, wie z. B. dem Tiltrotorflugzeug oder dem Hubschrauber, weist ein erfindungsgemäßes Fluggerät erhebliche Vorteile auf. So ist z. B. nicht, wie beim Hubschrauber, eine Neigung der Rotorebene notwendig um die Marschgeschwindigkeit zu verändern; die Probleme von Rotorblättern bei Hubschraubern insbesondere bei Hochleistungshubschraubern durch Erreichen der Schallgeschwindigkeit der Blattspitzen fallen weg; auf einen Ausgleichsrotor, wie den üblichen Heckrotor bei Hubschraubern kann verzichtet werden. Als wesentlicher Vorteil des erfindungsgemäßen Fluggeräts sei hervorgehoben, dass eine Änderung der Queranströmung der rotierenden Zylinder nach Größe und Richtung mit technisch wenig aufwendigen Mitteln verwirklichbar ist und somit besonders agiles Flugverhalten des Fluggeräts erreichbar ist.Compared to known short-start or vertical takeoff aircraft, such. As the Tiltrotorflugzeug or the helicopter, an inventive aircraft has significant advantages. So z. B. not, as in the helicopter, a tilt of the rotor plane necessary to change the marching speed; the problems of rotor blades in helicopters, especially in high-performance helicopters, by reaching the speed of sound of the blade tips fall away; on a balancing rotor, such as the usual tail rotor in helicopters can be omitted. As a major advantage of the aircraft according to the invention should be emphasized that a change in the Queranströmung the rotating cylinder size and direction with technically inexpensive means can be realized and thus particularly agile flight behavior of the aircraft is achievable.
Obwohl für die Queranströmung der rotierenden Zylinder jede Art von Gebläse einsetzbar ist, also z. B. ein Propellergebläse oder auch ein Axialgebläse nach Art eines sogenannten Fans, wie er bei modernen Strahltriebwerksflugzeugen zur Anwendung kommt, wird als bevorzugte Ausführungsform der Erfindung vorgeschlagen, ein Radialgebläse einzusetzen, dessen Tragflügelprofil aufweisende Rotorblätter um parallel zur Rotationsachse ausgerichtete Achsen schwenkbar sind. Durch diese Ausgestaltung hat man hervorragende Möglichkeiten den Querstrom nach Größe und Richtung exakt zu steuern.Although any type of fan can be used for the transverse flow of the rotating cylinder, so z. As a propeller blower or an axial fan in the manner of a so-called fans, as used in modern jet engine aircraft is used, is as a preferred embodiment of the invention proposed to use a radial fan, the wing profile having rotor blades are pivotable about axes aligned parallel to the axis of rotation. This configuration has excellent opportunities to control the cross flow size and direction exactly.
Aus der
Schließlich ist aus der
Finally, out of the
Eine besonders vorteilhafte Ausgestaltung erfährt die Erfindung dadurch, dass der Rotor des Radialgebläses jeweils den quer anzuströmenden rotierenden Zylinder mit Abstand konzentrisch umgibt. Dadurch entsteht jeweils eine aus Querstromgebläse und rotierendem Zylinder bestehende Antriebseinheit zur Erzeugung der gewünschten Auftriebs- bzw. Vortriebskräfte, die nicht nur als Ganzes platzsparende kompakte Bauweise gewährleistet, sondern darüber hinaus durch die konzentrische Anordnung die Antriebsmechanik für das Radialgebläse und für den rotierenden Zylinder in baulich einfacher und kompakter Weise zu gestalten erlaubt.A particularly advantageous embodiment, the invention undergoes the fact that the rotor of the radial fan surrounds each concentrically surrounding the rotating cylinder to be flowed in at a distance. This results in each case of a cross-flow fan and rotating cylinder existing drive unit for generating the desired buoyancy or driving forces, which not only ensures space-saving compact design as a whole, but also by the concentric arrangement of the drive mechanism for the Radial fan and for the rotating cylinder in a structurally simple and compact way to design.
Vorzugsweise soll der Radialabstand der rotierenden Rotorblätter von der Manteloberfläche des geschlossenen rotierenden Zylinders das Ein- bis Zweifache der Profiltiefe der Rotorblätter betragen. Der Durchmesser des Radialgebläserotors wiederum soll gemäß einer bevorzugten Ausführungsform der Erfindung das Fünf- bis Achtfache der Profiltiefe eines Rotorblattes betragen. Die Anzahl der für einen Radialgebläserotor einzusetzenden Rotorblätter soll mindestens zwei vorzugsweise acht betragen. Dabei soll in weiterer Ausbildung der Erfindung der Umfangsabstand der Rotorblätter des Radialgebläses zumindest so groß sein wie die Profiltiefe der Rotorblätter.Preferably, the radial distance of the rotating rotor blades from the mantle surface of the closed rotating cylinder should be one to two times the tread depth of the rotor blades. The diameter of the radial fan motor in turn should amount to five to eight times the tread depth of a rotor blade according to a preferred embodiment of the invention. The number of rotor blades to be used for a radial fan rotor should be at least two, preferably eight. It should be at least as large as the tread depth of the rotor blades in a further embodiment of the invention, the circumferential distance of the rotor blades of the radial fan.
Weiterhin ist es vorteilhaft, wenn die Anstellwinkel der Rotorblätter des Radialgebläses periodisch mit der Rotation gesteuert werden. Vorzugsweise erfolgt die Steuerung des Anstellwinkels der Rotorblätter zentral durch eine Exzenterkurbel mit zu den einzelnen Rotorblättern verlaufenden Steuerstangen. Alternativ kann jedoch auch eine Steuerung der Anstellwinkel der Rotorblätter über ein Stellgetriebe erfolgen, welches ein um die Rotorachse des Radialgebläses rotierendes Antriebsrad und mit diesem zusammenwirkende radial zu jedem einzelnen Rotorblatt verlaufende Steuerwellen umfasst. Die letztgenannte Ausgestaltung ist insbesondere dann vorteilhaft, wenn hohe Anströmgeschwindigkeiten und damit vergleichsweise hohe Drehzahlen des Radialgebläses verwirklicht werden sollen.Furthermore, it is advantageous if the angles of incidence of the rotor blades of the radial fan are controlled periodically with the rotation. Preferably, the control of the angle of attack of the rotor blades takes place centrally by an eccentric crank with extending to the individual rotor blades control rods. Alternatively, however, a control of the angle of attack of the rotor blades via a control gear can take place, which comprises a rotating about the rotor axis of the radial fan drive wheel and cooperating with this radially extending to each individual rotor blade control shafts. The latter embodiment is particularly advantageous when high flow velocities and thus comparatively high speeds of rotation of the radial fan are to be realized.
In weiterer Ausbildung der Erfindung wird vorgeschlagen, dass, wie an sich im Stand der Technik bekannt, die Rotorblätter des Radialgebläses zur Veränderung des Tragflügelprofils mehrteilig ausgebildet sind. Eine solche Ausbildung ist insbesondere dann von Vorteil, wenn auch ein Betrieb bei niedrigen Anströmgeschwindigkeiten in Betracht gezogen wird.In a further embodiment of the invention it is proposed that, as known per se in the prior art, the rotor blades of the radial fan are designed to change the wing profile in several parts. Such Training is particularly advantageous if an operation at low flow velocities is taken into consideration.
Schließlich soll bei bevorzugten Ausführungsformen der Erfindung sowohl die Drehrichtung der geschlossenen Zylinder änderbar sein als auch die Drehzahl der geschlossenen Zylinder unabhängig von der Drehzahl des Radialgebläses einstellbar sein.Finally, in preferred embodiments of the invention, both the direction of rotation of the closed cylinder should be changeable and the rotational speed of the closed cylinder should be adjustable independently of the rotational speed of the radial fan.
Bevorzugt sind bei einem Fluggerät symmetrisch zum Nutzlastrumpf beidseitig aus Querstromgebläse und rotierendem Zylinder bestehende Antriebseinheiten angeordnet. Durch deren exakte Steuerung kann eine Verschwenkung des Fluggeräts um dessen Längsachse bei Kurvenflug eingestellt werden. Schließlich ist es vorteilhaft, wenn ein Fluggerät zumindest zwei in Längsrichtung voneinander beabstandete, aus Querstromgebläse und rotierendem Zylinder bestehende Antriebseinheitenpaare aufweist.Preferably, in an aircraft symmetrical to Nutzlastrumpf arranged on both sides of cross-flow fan and rotating cylinder existing drive units. Due to their precise control, a pivoting of the aircraft can be adjusted about its longitudinal axis when turning. Finally, it is advantageous if an aircraft has at least two drive unit pairs which are spaced apart from each other in the longitudinal direction and comprise cross-flow fans and rotating cylinders.
Durch entsprechende Steuerung der in Längsrichtung beabstandeten Antriebseinheitenpaare wird dann eine Schwenkung des Fluggeräts um seine Querachse und/oder Hochachse erzielt.By appropriate control of the longitudinally spaced pairs of drive units, a pivoting of the aircraft about its transverse axis and / or vertical axis is then achieved.
Weitere vorteilhafte Ausgestaltungen der Erfindung entsprechend der Ansprüche 16 bis 18 werden im Rahmen der Beschreibung von Ausführungsbeispielen weiter unten erläutert.Further advantageous embodiments of the invention according to the claims 16 to 18 are explained below in the description of embodiments below.
Anhand der beigefügten Zeichnungen werden Ausführungsbeispiele der Erfindung erläutert. In den Zeichnungen zeigt
- Fig. 1
- eine erste erfindungsgemäße Ausführungsform eines Fluggeräts mit zwei in Längsrichtung des Fluggeräts beabstandeten, aus Querstromgebläse und rotierendem Zylinder bestehenden Antriebseinheitenpaaren im Schrägbild,
- Fig. 2
- eine schematische Darstellung einer aus Gebläse und rotierendem Zylinder bestehenden Antriebseinheit,
- Fig. 2a
- eine schematische Darstellung einer Antriebseinheit entsprechend
Fig. 2 , wobei das Gebläse sich in Strömungsrichtung hinter dem rotierenden Zylinder befindet. - Fig. 2b
- eine schematische Darstellung einer Antriebseinheit nach
Fig. 2a , wobei als Gebläse ein translatorisch quer zur Strömungsrichtung bewegter Tragflügel vorgesehen ist. - Fig. 2c
- eine schematische Darstellung der Antriebseinheit, entsprechend
Fig. 2b , bei welcher der Tragflügel für translatorische und rotatorische Bewegung angepasst ist., - Fig. 3a
- eine aus Radialgebläse und konzentrisch darin angeordnetem rotierendem Zylinder bestehende Antriebseinheit im Querschnitt schematisch,
- Fig. 3b
- die Antriebseinheit gemäß
Fig. 3a bei verändertem Anstellwinkel der Rotorblätter, - Fig. 4
- eine Darstellung entsprechend den
Fig. 3a ,3b , jedoch mit eingezeichneten Bewegungs- und Kraftgrößen, - Fig. 5
- ein Stellgetriebe für die Steuerung des Anstellwinkels der Rotorblätter schematisch,
- Fig. 6
- mehrteilig ausgebildete Rotorblätter eines Radialgebläses schematisch,
- Fig. 7
- eine weitere Ausführungsform eines erfindungsgemäßen Fluggerätes in Schrägbilddarstellung entsprechend
Fig. 1 und - Fig. 8
- eine dritte Ausführungsform eines erfindungsgemäßen Fluggerätes in Schrägbilddarstellung entsprechend
Fig. 7 . - Fig. 9
- die schematische Schrägbilddarstellung einer weiteren Ausführungsform eines rotierenden Zylinders 1 nach
Fig. 2 mit drei Scheiben, deren Durchmesser da größer ist als der Zylinderdurchmesser di, - Fig. 10
- eine Antriebseinheit gemäß
Fig. 3a , mit einem rotierenden Zylinder der Ausführungsform nachFig. 9 im Schrägbild schematisch.
- Fig. 1
- a first embodiment of an aircraft according to the invention with two spaced apart in the longitudinal direction of the aircraft, from Cross-flow fan and rotating cylinder existing drive unit pairs in the oblique view,
- Fig. 2
- a schematic representation of an existing blower and rotating cylinder drive unit,
- Fig. 2a
- a schematic representation of a drive unit accordingly
Fig. 2 with the blower downstream of the rotating cylinder. - Fig. 2b
- a schematic representation of a drive unit according to
Fig. 2a , wherein as fan a translationally transversely to the flow direction moving wing is provided. - Fig. 2c
- a schematic representation of the drive unit, accordingly
Fig. 2b in which the wing is adapted for translational and rotational movement. - Fig. 3a
- a drive unit consisting of a radial fan and concentrically arranged therein rotating cylinder in cross-section,
- Fig. 3b
- the drive unit according to
Fig. 3a with changed angle of attack of the rotor blades, - Fig. 4
- a representation according to the
Fig. 3a .3b , but with marked movement and force variables, - Fig. 5
- a control gear for the control of the angle of attack of the rotor blades schematically,
- Fig. 6
- multi-part rotor blades of a radial fan schematically,
- Fig. 7
- a further embodiment of an aircraft according to the invention in an oblique view corresponding
Fig. 1 and - Fig. 8
- a third embodiment of an aircraft according to the invention in an oblique view corresponding
Fig. 7 , - Fig. 9
- the schematic oblique view of another embodiment of a
rotating cylinder 1 afterFig. 2 with three disks whose diameter is larger than the cylinder diameter di, - Fig. 10
- a drive unit according to
Fig. 3a , with a rotating cylinder of the embodiment according toFig. 9 in the oblique image schematically.
Das in
In
In
In
Durch Steuerung der Queranströmung 8 nach Richtung und Größe und durch Steuerung der Drehzahl des rotierenden Zylinders 1 kann auch hier die Antriebskraft aus dem rotierenden Zylinder 1 eingestellt werden.In
By controlling the
In
Durch Steuerung der Queranströmung 8 nach Richtung und Größe und durch Steuerung der Drehzahl des rotierenden Zylinders 1 kann auch hier die Antriebskraft aus dem rotierenden Zylinder 1 eingestellt werden.In
By controlling the
Die in den
In der schematischen Darstellung gemäß
Die Schrägbilddarstellungen gemäß
Die in
Die Schrägbilddarstellung gemäß
Die schematische Schrägbilddarstellung gemäß
Claims (18)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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DE102007009951A DE102007009951B3 (en) | 2007-03-01 | 2007-03-01 | Aircraft e.g. helicopter, has radial blower with adjustable driving power assigned to each cylinder for generating air flow that flows transversely against cylinder, where rotor of blower concentrically surrounds cylinder with distance |
Publications (1)
Publication Number | Publication Date |
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EP1964774A2 true EP1964774A2 (en) | 2008-09-03 |
Family
ID=39494720
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP08003540A Withdrawn EP1964774A2 (en) | 2007-03-01 | 2008-02-27 | Flying device with rotating cylinders for generating lift and/or thrust |
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Country | Link |
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EP (1) | EP1964774A2 (en) |
DE (1) | DE102007009951B3 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102616376A (en) * | 2010-12-22 | 2012-08-01 | 伊德斯德国股份有限公司 | Hybrid rotor |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2511177B1 (en) * | 2011-04-11 | 2013-06-05 | Eurocopter Deutschland GmbH | Helicopter with cycloidal rotor system |
US10106253B2 (en) * | 2016-08-31 | 2018-10-23 | Bell Helicopter Textron Inc. | Tilting ducted fan aircraft generating a pitch control moment |
DE102017011890B4 (en) * | 2017-12-14 | 2023-02-09 | Cyclotech Gmbh | Propulsion device for an aircraft |
DE102021003751B3 (en) | 2021-07-20 | 2022-11-24 | Friedrich B. Grimm | VEHICLE WITH A ROTARY WING KINEMATICS |
DE102021004136B4 (en) | 2021-08-09 | 2023-03-09 | Friedrich B. Grimm | Device for a rotary wing vehicle or for a rotary wing turbine |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3615089A1 (en) | 1986-05-03 | 1987-11-05 | Wolfram Wittenborn | Aircraft having roller wings |
DE69000474T2 (en) | 1989-04-17 | 1993-07-01 | Servanty Brives Marthe | ROTOR, SUITABLE FOR GENERATING AN OPERATION AND / OR DRIVING IN A LIQUID, METHOD FOR CONTROLLING AND AIRPLANE THAT IS EQUIPPED WITH IT. |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1665533A (en) * | 1925-10-22 | 1928-04-10 | Ovid L Dally | Aerial vessel |
DE19529700A1 (en) * | 1995-08-11 | 1997-02-13 | Pflug Jochen Dipl Ing Fh | Aircraft with rotating wings - uses adjustment of left and right control points to determine drive and thrust |
DE19715827A1 (en) * | 1997-04-16 | 1998-10-22 | Peter Dr Faber | Aircraft taking off and landing vertically |
DE102004007682A1 (en) * | 2003-11-16 | 2005-06-23 | Ip2H Ag | aircraft |
DE202004017902U1 (en) * | 2004-11-11 | 2005-06-02 | Pommerening, Ingo, Prof. Dr. | Airplane comprises devices known as Flettner rotors arranged at right angles to the fuselage and which rotate so that the flow is accelerated and a low pressure is produced on the upper side |
-
2007
- 2007-03-01 DE DE102007009951A patent/DE102007009951B3/en not_active Expired - Fee Related
-
2008
- 2008-02-27 EP EP08003540A patent/EP1964774A2/en not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3615089A1 (en) | 1986-05-03 | 1987-11-05 | Wolfram Wittenborn | Aircraft having roller wings |
DE69000474T2 (en) | 1989-04-17 | 1993-07-01 | Servanty Brives Marthe | ROTOR, SUITABLE FOR GENERATING AN OPERATION AND / OR DRIVING IN A LIQUID, METHOD FOR CONTROLLING AND AIRPLANE THAT IS EQUIPPED WITH IT. |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102616376A (en) * | 2010-12-22 | 2012-08-01 | 伊德斯德国股份有限公司 | Hybrid rotor |
CN102616376B (en) * | 2010-12-22 | 2015-11-25 | 伊德斯德国股份有限公司 | Composite rotors |
Also Published As
Publication number | Publication date |
---|---|
DE102007009951B3 (en) | 2008-07-31 |
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